Landing gear mechanism for use on rough runways
US4552324A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | May 31, 1983 |
| Grant date | Nov 12, 1985 |
| Priority date | — |
| Expiry date | May 31, 2003 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16F9/512
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
Landing gear mechanism includes a built-in hydraulic actuator which may be actuated to provide a heavy load range, soft spring rate during take-off with a heavy take-off weight and a lower load range, softer spring rate after take-off and prior to landing with a lighter landing weight to yield more shock strut stroke for a given range of vertical load during landing. A special taxi valve allows for some fluid to bypass the main orifice more freely to and from the lower piston damping chamber to the shock strut air-oil chamber as soon as the landing energy stroke is complete to greatly reduce or eliminate high damping loads that might otherwise take place as the gear negotiates bumps. Such a valve may automatically be set to close for landing by the action of the gear extension during a subsquent take-off, thus reactivating the main orifice. For normal bounce, air in the primary chamber drives oil through an orifice in a rebound damper valve to the lower piston chamber in order to lift the supported weight of the aircraft as part of the return stroke. However, when riding over a hole, the air acts freely on the differential or net piston area of the gear which area is too small to l…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.